Numerical Investigation of Stall Flutter
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Authors
Ekaterinaris, J.A.
Platzer, M.F.
Subjects
Advisors
Date of Issue
1996-04
Date
April 1996
Publisher
ASME
Language
Abstract
Unsteady, separated, high Reynolds number flow over an airfoil undergoing oscillatory
motion is investigated numerically. The compressible form of the Reynolds-averaged
governing equations is solved using a high-order, upwind biased numerical
scheme. The turbulent flow region is computed using a one-equation turbulence
model. The computed results show that the key to the accurate prediction of the
unsteady loads at stall flutter conditions is the modeling of the transitional flow
region at the leading edge. A simplified criterion for the transition onset is used. The
transitional flow region is computed with a modified form of the turbulence model.
The computed solution, where the transitional flow region is included, shows that
the small laminar/transitional separation bubble forming during the pitch-up motion
has a decisive effect on the near-wall flow and the development of the unsteady loads.
Detailed comparisons of computed fully turbulent and transitional flow solutions with
experimental data are presented.
Type
Article
Description
Series/Report No
Department
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Naval Warfare Center, Weapons Division, China Lake CA
Naval Postgraduate School Internal Research Program
Naval Postgraduate School Internal Research Program
Funder
Naval Warfare Center, Weapons Division, China Lake CA
Naval Postgraduate School Internal Research Program
Naval Postgraduate School Internal Research Program
Format
7 p.
Citation
Journal of Turbomachinery
April 1996, Vol. 118 p. 197-203
Distribution Statement
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.